An assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure extends circumferentially about the rotating structure. The stationary structure is configured from or otherwise includes stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F. The bushing is radially between the rotating structure and the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F. The mount material contacts the stationary structure material. The bearing is configured from or otherwise includes bearing material, where the bearing material is engaged with and rotatably supports the rotating structure. The bearing material is or otherwise includes copper.
|
19. An assembly for a gas turbine engine, comprising:
a rotating structure extending axially along and rotatable about a centerline;
a stationary structure circumscribing the rotating structure, the stationary structure comprising at least one of aluminum or magnesium; and
a bushing rotatably coupling the rotating structure to the stationary structure, the bushing including a mount and a bearing within the mount, the mount comprising stainless steel that contacts the at least one of the aluminum or the magnesium, and the bearing comprising leaded bronze that is engaged with and rotatably supports the rotating structure;
wherein the bushing further includes a sleeve radially between the mount and the bearing; and
wherein the sleeve comprises plain carbon steel contacting the stainless steel and the leaded bronze.
14. An assembly for a gas turbine engine, comprising:
a rotating structure extending axially along and rotatable about a centerline;
a stationary structure extending circumferentially about the rotating structure, the stationary structure comprising stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F.; and
a bushing radially between the rotating structure and the stationary structure, the bushing including a mount and a bearing within the mount, the mount comprising mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F., the mount material contacting the stationary structure material, the bearing comprising bearing material engaged with and rotatably supporting the rotating structure, and the bearing material comprising copper;
wherein the bearing material contacts and is bonded to the mount material.
1. An assembly for a gas turbine engine, comprising:
a rotating structure extending axially along and rotatable about a centerline;
a stationary structure extending circumferentially about the rotating structure, the stationary structure comprising stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F.; and
a bushing radially between the rotating structure and the stationary structure, the bushing including a mount and a bearing within the mount, the mount comprising mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F., the mount material contacting the stationary structure material, the bearing comprising bearing material engaged with and rotatably supporting the rotating structure, and the bearing material comprising copper;
wherein the bushing further includes a sleeve radially between the mount and the bearing;
wherein the sleeve comprises sleeve material with a coefficient of thermal expansion between 6 μin/in-° F. and 7 μin/in-° F.; and
wherein the sleeve material contacts the mount material and the bearing material.
6. The assembly of
201 stainless steel;
203 stainless steel;
204 stainless steel;
209 stainless steel;
214 stainless steel;
216 stainless steel;
218 stainless steel; or
240 stainless steel.
8. The assembly of
302 stainless steel;
303 stainless steel;
304 stainless steel;
310 stainless steel;
316 stainless steel;
321 stainless steel; or
347 stainless steel.
9. The assembly of
the bearing material comprises bronze; and
the bronze comprises the copper.
11. The assembly of
the mount includes a base and a flange;
the base is disposed within an aperture of the stationary structure and radially contacts the stationary structure; and
the flange projects radially out from the base and axially engages the stationary structure.
15. The assembly of
17. The assembly of
the bearing material comprises bronze; and
the bronze comprises the copper.
18. The assembly of
the mount includes a base and a flange;
the base is disposed within an aperture of the stationary structure and radially contacts the stationary structure; and
the flange projects radially out from the base and axially engages the stationary structure.
20. The assembly of
the mount includes a base and a flange;
the base is mated with an aperture of the stationary structure; and
the flange projects radially out from the base and axially engages the stationary structure.
|
|||||||||||||||||||||||||||
This disclosure relates generally to a gas turbine engine and, more particularly, to a bushing for the gas turbine engine.
A gas turbine engine may include a shaft rotatably mounted to a housing by a bushing. The shaft may rotate within the bushing such that the shaft and the bushing form a journal bearing. Various types and configurations of journal bearing bushings are known in the art. While these known journal bearing bushings have various benefits, there is still room in the art for improvement. There is a need in the art therefore for an improved bushing for rotatably mounting a rotating structure such as a shaft to a stationary structure such as a housing.
According to an aspect of the present disclosure, an assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure extends circumferentially about the rotating structure. The stationary structure is configured from or otherwise includes stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F. The bushing is radially between the rotating structure and the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F. The mount material contacts the stationary structure material. The bearing is configured from or otherwise includes bearing material, where the bearing material is engaged with and rotatably supports the rotating structure. The bearing material is or otherwise includes copper.
According to another aspect of the present disclosure, another assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure circumscribes the rotating structure. The stationary structure is configured from or otherwise includes at least one of the aluminum or the magnesium. The bushing rotatably couples the rotating structure to the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes stainless steel, where the stainless steel contacts the at least one of the aluminum or the magnesium. The bearing is configured from or otherwise includes leaded bronze, where the leaded bronze is engaged with and rotatably supports the rotating structure.
According to still another aspect of the present disclosure, another assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure circumscribes the rotating structure. The stationary structure is configured from or otherwise includes stationary structure material. The stationary structure material is or otherwise includes at least one of aluminum or magnesium. The bushing rotatably couples the rotating structure to the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes mount material, where the mount material contacts the stationary structure material. The bearing is configured from or otherwise includes bronze, where the bronze is engaged with and rotatably supports the rotating structure. The mount material is or otherwise includes at least one of 200 series stainless steel or 300 series stainless steel.
The leaded bronze may contact the stainless steel.
The bushing may also include a sleeve radially between the mount and the bearing. The sleeve may be configured from or otherwise include plain carbon steel contacting the stainless steel and the leaded bronze.
The mount may include a base and a flange. The base may be mated with an aperture of the stationary structure. The flange may project radially out from the base and may axially engage the stationary structure.
The stationary structure material may be or otherwise include aluminum.
The stationary structure material may be or otherwise include magnesium.
The mount material may be or otherwise include stainless steel.
The stainless steel may be or otherwise include 200 series stainless steel.
The stainless steel may be or otherwise include one of: 201 stainless steel; 203 stainless steel; 204 stainless steel; 209 stainless steel; 214 stainless steel; 216 stainless steel; 218 stainless steel; or 240 stainless steel.
The stainless steel may be or otherwise include 300 series stainless steel.
The stainless steel may be or otherwise include one of: 302 stainless steel; 303 stainless steel; 304 stainless steel; 310 stainless steel; 316 stainless steel; 321 stainless steel; or 347 stainless steel.
The bearing material may be configured from or otherwise include bronze, where the bronze includes the copper.
The bronze may be or otherwise include leaded bronze.
The bearing material may contact the mount material.
The bushing may also include a sleeve radially between the mount and the bearing. The sleeve may be configured from or otherwise include sleeve material with a coefficient of thermal expansion between 6 μin/in-° F. and 7 μin/in-° F. The sleeve material may contact the mount material and the bearing material.
The mount may include a base and a flange. The base may be disposed within an aperture of the stationary structure and may radially contact the stationary structure. The flange may project radially out from the base and may axially engage the stationary structure.
The rotating structure may be configured as or otherwise include a shaft.
The rotating structure may be configured as or otherwise include a gear.
The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof.
The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings.
The engine assembly 10 of
The rotating structure 12 extends axially along an axial centerline 18 to an axial end 20 of the rotating structure 12. The rotating structure 12 extends circumferentially about (e.g., completely around) the axial centerline 18. The rotating structure 12 extends radially outward (e.g., away from the axial centerline 18) to a radial outer side 22 of the rotating structure 12.
The rotating structure 12 is rotatable about the axial centerline 18; e.g., a rotational axis. This rotating structure 12 may be configured as a rotor for an apparatus within the gas turbine engine such as a geartrain 24. The rotating structure 12 of
The rotating structure 12 is constructed from or otherwise includes rotating structure material. This rotating structure material is a metal such as a high strength, low alloy steel; e.g., AISI 9310, AISI 4340 and AISI 17-22A. The rotating structure material may be selected to have a coefficient of thermal expansion between 6.5 μin/in-° F. (˜11.7 μm/m-° C.) and 7.0 μin/in-° F. (˜12.6 μm/m-° C.); e.g., 6.9 μin/in-° F. (˜12.42 μm/m-° C.) for AISI 9310, 6.5 μin/in-° F. (˜11.7 μm/m-° C.) for AISI 4340, or 7.0 μin/in-° F. (˜12.6 μm/m-° C.) for AISI 17-22A. The coefficient of thermal expansion may be measured at 400° F.
The stationary structure 14 extends axially along the axial centerline 18 between and to an axial first side 30 of the stationary structure 14 and an axial second side 32 of the stationary structure 14. The stationary structure 14 extends circumferentially about (e.g., completely around) the axial centerline 18. The stationary structure 14 extends radially inwards (e.g., towards the axial centerline 18) to a radial inner side 34 of the stationary structure 14. This stationary structure inner side 34 forms an aperture 36 (e.g., a bore) within the stationary structure 14. The stationary structure aperture 36 of
The stationary structure 14 is configured as a support for the rotating structure 12 and the bushing 16. The stationary structure 14 may also be configured as a housing for the rotating structure 12 and/or one or more the other components of the engine assembly 10. The stationary structure 14, for example, may be configured as a geartrain housing with a leg or wall that supports the rotating structure 12 through the bushing 16 as described below. The present disclosure, however, is not limited to such an exemplary stationary structure configuration.
The stationary structure 14 is constructed from or otherwise includes stationary structure material. This stationary structure material is a high thermal expansion and/or lightweight metal such as aluminum (Al), magnesium (Mg), and/or an alloy thereof. The stationary structure material is selected to have a coefficient of thermal expansion between 10 μin/in-° F. (˜18 μm/m-° C.) and 15 μin/in-° F. (˜27 μm/m-° C.); e.g., between 10 μin/in-° F. (˜18 μm/m-° C.) and 12 μin/in-° F. (˜21.6 μm/m-° C.), between 12 μin/in-° F. (˜21.6 μm/m-° C.) and 13 μin/in-° F. (˜23.4 μm/m-° C.), between 13 μin/in-° F. (˜23.4 μm/m-° C.) and 15 μin/in-° F. (˜27 μm/m-° C.), etc. For example, the aluminum stationary structure material may be cast C355/355 (13 μin/in-° F.), A357/F357 (12.6 μin/in-° F.) or A356/356 (12.5 μin/in-° F.). The magnesium stationary structure material may be cast ZE41A (15.1 μin/in-° F.), WE43A (15.6 μin/in-° F.) or EV31A (14 μin/in-° F.). The coefficient of thermal expansion may be measured at 400° F.
Referring to
The mount 46 of
The base 50 and the flange 52 of
The mount 46 is constructed from or otherwise includes mount material. This mount material is a high thermal expansion metal such as stainless steel (ss). This stainless steel may be 200 series stainless steel such as, but not limited to: 201 stainless steel; 203 stainless steel; 204 stainless steel; 209 stainless steel; 214 stainless steel; 216 stainless steel; 218 stainless steel; or 240 stainless steel. The stainless steel may alternatively be 300 stainless steel such as, but not limited to: 302 stainless steel; 303 stainless steel; 304 stainless steel; 310 stainless steel; 316 stainless steel; 321 stainless steel; or 347 stainless steel. The mount material is selected to have a coefficient of thermal expansion between 9 μm/in-° F. (˜16.2 μm/m-° C.) and 10 μm/in-° F. (˜18 μm/m-° C.); e.g., between 9 μm/in-° F. (˜16.2 μm/m-° C.) and 9.5 μm/in-° F. (˜17.1 μm/m-° C.), between 9.5 μm/in-° F. (˜17.1 μm/m-° C.) and 10 μm/in-° F. (˜18 μm/m-° C.), etc. The coefficient of thermal expansion may be measured at 400° F.
The bearing 48 extends axially along the axial centerline 18 between and to an axial first side 66 of the bearing 48 and the bushing second side 40, where the bearing first side 66 may be recessed axially inward from the bushing first side 38 and/or axially aligned with the base first side 54. The bearing 48 extends circumferentially about (e.g., completely around) the axial centerline 18. The bearing 48 extends radially between and to the bushing inner side 42 and a radial outer side 68 of the bearing 48.
The bearing 48 is constructed from or otherwise includes bearing material. This bearing material is a high strength, low friction metal that includes copper; e.g., a copper alloy. The bearing material, for example, may be bronze such as, but not limited to, leaded bronze. The bearing material may have a coefficient of thermal expansion between 10.5 μm/in-° F. (˜18.9 μm/m-° C.) and 11.5 μm/in-° F. (˜20.7 μm/m-° C.); e.g., 10.9 μm/in-° F. (˜19.62 μm/m-° C.). The coefficient of thermal expansion may be measured at 400° F.
The bearing 48 is disposed within an aperture 70 (e.g., a bore) of the mount 46 and its base 50. The bearing 48 of
In addition to providing a material property bridge, the mount material may be selected such that the bearing material may be bonded (e.g., applied) to the mount material without degrading material properties of the mount material. For example, the mount material may be a non-hardenable stainless steel (e.g., the above disclosed 200 or 300 series stainless steels) such that heat used during the bonding and/or application of the bearing material to the mount material will not degrade or undo previous hardening of the mount material. More particularly, the mount material may be selected such that the mount material does not need to be hardened via heat treatment prior to receiving the bearing material.
The bushing 16 extends circumferentially about (e.g., completely around) the rotating structure 12 and its shaft 26; see also
In some embodiments, referring to
The sleeve material is selected to provide an additional material property bridge between the bearing material and the mount material. The sleeve material, for example, may be a low thermal expansion metal such as, but not limited to, plain carbon steel. The sleeve material is selected to have a coefficient of thermal expansion between 6 μin/in-° F. (˜10.8 μm/m-° C.) and 7 μin/in-° F. (˜12.6 μm/m-° C.). Inclusion of such a sleeve may be particularly useful where, for example, the mount material is a hardened stainless steel such as, but not limited to, hardened 286 stainless steel. The bearing material, for example, may be bonded and/or otherwise applied to the sleeve material. This coated sleeve may then be mounted (e.g., press fit or otherwise attached) to the mount 46 and its base 50 without, for example, affecting a hardness of the mount material.
The airflow inlet 86 is towards the engine aft end 84, and aft of the turbine engine sections 88-91. The exhaust 87 is located towards the engine forward end 82, and axially between propulsor section 88 and the turbine engine sections 89-91.
The propulsor section 88 includes a propulsor rotor 94; e.g., a propeller. The compressor section 89 includes a compressor rotor 96. The turbine section 91 includes a high pressure turbine (HPT) rotor 98 and a low pressure turbine (LPT) rotor 100, where the LPT rotor 100 may be referred to as a power turbine rotor and/or a free turbine rotor. Each of these turbine engine rotors 94, 96, 98 and 100 includes a plurality of rotor blades arranged circumferentially about and connected to one or more respective rotor disks or hubs.
The propulsor rotor 94 of
During gas turbine engine operation, air enters the gas turbine engine 78 through the airflow inlet 86. This air is directed into a core flowpath which extends sequentially through the engine sections 89-91 (e.g., an engine core) to the exhaust 87. The air within this core flowpath may be referred to as “core air”.
The core air is compressed by the compressor rotor 96 and directed into a combustion chamber of a combustor 110 in the combustor section 90. Fuel is injected into the combustion chamber and mixed with the compressed core air to provide a fuel-air mixture. This fuel-air mixture is ignited and combustion products thereof flow through and sequentially cause the HPT rotor 98 and the LPT rotor 100 to rotate. The rotation of the HPT rotor 98 drives rotation of the compressor rotor 96 and, thus, compression of air received from the airflow inlet 86. The rotation of the LPT rotor 100 drives rotation of the propulsor rotor 94, which propels air outside of the gas turbine engine 78 in an aft direction to provide forward thrust. The present disclosure, however, is not limited to any particular types or configurations of gas turbine engines as stated above.
While various embodiments of the present disclosure have been described, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.
| Patent | Priority | Assignee | Title |
| Patent | Priority | Assignee | Title |
| 4427309, | Mar 24 1980 | The Garrett Corporation | Turbocharger shaft bearing |
| 5538349, | Mar 13 1995 | Eaton Corporation | Bayonet bearing retainer |
| 6010246, | Oct 25 1995 | SANKYO SEIKI MFG CO , LTD | Hydrodynamic bearing apparatus and method of manufacturing it |
| 6293263, | Oct 30 1998 | Vortech Engineering, Inc. | Compact supercharger with improved lubrication |
| 7108488, | Mar 26 2004 | JPMORGAN CHASE BANK, N A , AS ADMINISTRATIVE AGENT | Turbocharger with hydrodynamic foil bearings |
| 7492548, | Apr 24 2003 | PHC HOLDINGS CORPORATION | Hydrodynamic bearing device and disk rotating apparatus |
| 20050210875, | |||
| 20060032225, | |||
| 20130089418, | |||
| 20150049967, | |||
| 20150056065, | |||
| 20170310188, | |||
| 20190368548, | |||
| 20210310420, | |||
| DE102011079677, | |||
| DE102016211807, | |||
| JP2013015033, | |||
| JP8170646, | |||
| JP830492, |
| Executed on | Assignor | Assignee | Conveyance | Frame | Reel | Doc |
| Apr 18 2022 | Pratt & Whitney Canada Corp. | (assignment on the face of the patent) | / | |||
| Apr 29 2022 | BELANGER, JEAN-FRANCOIS | Pratt & Whitney Canada Corp | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 060303 | /0695 |
| Date | Maintenance Fee Events |
| Apr 18 2022 | BIG: Entity status set to Undiscounted (note the period is included in the code). |
| Date | Maintenance Schedule |
| Sep 12 2026 | 4 years fee payment window open |
| Mar 12 2027 | 6 months grace period start (w surcharge) |
| Sep 12 2027 | patent expiry (for year 4) |
| Sep 12 2029 | 2 years to revive unintentionally abandoned end. (for year 4) |
| Sep 12 2030 | 8 years fee payment window open |
| Mar 12 2031 | 6 months grace period start (w surcharge) |
| Sep 12 2031 | patent expiry (for year 8) |
| Sep 12 2033 | 2 years to revive unintentionally abandoned end. (for year 8) |
| Sep 12 2034 | 12 years fee payment window open |
| Mar 12 2035 | 6 months grace period start (w surcharge) |
| Sep 12 2035 | patent expiry (for year 12) |
| Sep 12 2037 | 2 years to revive unintentionally abandoned end. (for year 12) |